摘要
对锐边高超声速再入飞行器气动隐身综合设计进行了研究。以REX-203飞行器外形为研究对象建模,分析了修正牛顿理论、活塞理论和激波膨胀波理论三种常用的高超声速气动力工程算法用于锐边高超声速再入飞行器的适用性,用最准确的修正牛顿理论讨论了不同外形的飞行器最大升阻比变化规律,用高频近似算法计算了飞行器雷达散射面积（RCS）。综合考虑最大升阻比和RCS,给出飞行器隐身气动综合优化设计为飞行器中部长度0.6-0.7m。
The comprehensive design of sharp-edged hypersonic re-entry vehicles was studied in this paper.The shape of REX-203 vehicle was used as the study object and was modeled.The applicability and the accuracy of the three engineering algorithms which were modified Newtonian theory,piston theory and shock-expansion method were analyzed.The variation of the maximum lift-to-drag was analyzed with various shapes using modified Newtonian theory which was the most accuracy in the three.The radar cross section（RCS）of the vehicle was computed using the high-frequency approximation.The optimization design was that the middle length of the vehicle was 0.6to 0.7m with the integration of maximum lift-to-drag and RCS.
出处
《上海航天》
2016年第2期100-105,共6页
Aerospace Shanghai
关键词
锐边高超声速再入飞行器
气动
隐身
综合设计
修正牛顿理论
外形
最大升阻比
雷达散射面积
Sharp-edge hypersonic re-entry vehicle
Aerodynamic
Stealth
Comprehensive design
Modified Newtonian theory
Shape
Maximum lift-to-drag
Radar cross section
